EP3477050A1 - Asymmetrisch konturierter strömungsring für verdichter einer strömungsmaschine - Google Patents

Asymmetrisch konturierter strömungsring für verdichter einer strömungsmaschine Download PDF

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Publication number
EP3477050A1
EP3477050A1 EP18195628.5A EP18195628A EP3477050A1 EP 3477050 A1 EP3477050 A1 EP 3477050A1 EP 18195628 A EP18195628 A EP 18195628A EP 3477050 A1 EP3477050 A1 EP 3477050A1
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EP
European Patent Office
Prior art keywords
blade
compressor
boss
recess
inter
Prior art date
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Granted
Application number
EP18195628.5A
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English (en)
French (fr)
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EP3477050B1 (de
Inventor
Stéphane Hiernaux
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aero Boosters SA
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Safran Aero Boosters SA
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Publication of EP3477050A1 publication Critical patent/EP3477050A1/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/123—Fluid guiding means, e.g. vanes related to the pressure side of a stator vane
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/124—Fluid guiding means, e.g. vanes related to the suction side of a stator vane
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/712—Shape curved concave
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a hump and hollow geometry in an inter-blade passage of a turbomachine compressor.
  • the invention also relates to an axial turbomachine, in particular an aircraft turbojet engine or an aircraft turboprop engine.
  • the document FR3011888 A1 discloses a turbojet engine with a compressor part comprising at least first and second blades, and a platform from which the blades extend.
  • the platform has a non-axisymmetric surface limited by a first and a second extremal plane, and defined by at least two class CI construction curves each representing the value of a radius of said surface as a function of a position between the intrados of the first blade and the extrados of the second blade in a plane substantially parallel to the extremal planes.
  • This particular non-axisymmetric geometry of the surface of the part offers a control of the flow, however it limits the flow, in particular because of detachments in blade corners. Pumping phenomena can occur.
  • the object of the invention is to solve at least one of the problems posed by the prior art. More specifically, the invention aims to optimize the flow rate and the compression ratio of a compressor. The invention also aims to provide a simple solution, resistant, lightweight, economical, reliable, easy to produce, convenient maintenance, and easy inspection.
  • the subject of the invention is an axial turbomachine compressor, in particular an axial turbomachine low-pressure compressor, the compressor comprising: an annular vein; a first dawn with a surface soffit; a second blade with an extrados surface facing the intrados surface of the first blade; an inter-vane passage with a guiding surface which connects the intrados surface to the extrados surface radially delimiting the annular vein, and which has a main boss and a main recess; remarkable in that the guide surface comprises an axially symmetrical or substantially planar zone which passes axially through the inter-blade passage so as to separate, and in particular to connect, the main hollow of the main boss.
  • the boss extends circumferentially from the extrados surface of the second blade, and includes a crown against the extrados surface.
  • the hollow extends circumferentially from the intrados surface of the first blade, and comprises a bottom against the intrados surface.
  • the hump is convex and the hollow is concave.
  • the invention also relates to a turbine engine compressor blade, the blade comprising a fixing platform which comprises a guide surface of a compressor flow, and two lateral edges intended to marry.
  • a fixing platform which comprises a guide surface of a compressor flow, and two lateral edges intended to marry.
  • the subject of the invention is also a turbomachine, in particular an aircraft turbojet, comprising a compressor and / or at least one blade, which is remarkable in that the compressor is in accordance with the invention and / or the blade is in conformity with the invention. 'invention.
  • each object of the invention is also applicable to the other objects of the invention.
  • Each object of the invention is combinable with other objects, and the objects of the invention are also combinable with the embodiments of the description.
  • the terms “internal” and “external” refer to a positioning relative to the axis of rotation of an axial turbomachine.
  • the axial direction corresponds to the direction along the axis of rotation of the turbomachine, the lengths being measured axially. The widths are measured according to the circumference.
  • the radial direction is perpendicular to the axis of rotation. Upstream and downstream are in reference to the main flow direction of the flow in the turbomachine.
  • the figure 1 represents in simplified manner an axial turbomachine. It is in this case a double-flow turbojet engine.
  • the turbojet engine 2 comprises a low-pressure compressor 4, a high-pressure compressor 6, a combustion chamber 8 and one or more turbine levels 10.
  • the mechanical power of the turbine 10 transmitted via the central shaft up to the rotor 12 sets in motion the two compressors 4 and 6.
  • the latter comprise several rows of rotor blades associated with rows of stator vanes.
  • the rotation of the rotor about its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until it reaches the combustion chamber 8.
  • a blower 16 is coupled to the rotor 12 and generates a stream of air which splits into a primary stream 18 and a secondary stream 20 passing through an annular duct (partially shown). The secondary flow is accelerated to generate a thrust response useful to the flight of an aircraft.
  • the primary 18 and secondary 20 streams are annular.
  • the figure 2 is a sectional view of a compressor of an axial turbomachine such as that of the figure 1 .
  • the compressor may be the low-pressure compressor 4. There may be observed a portion of the blower 16 and the separation nozzle 22 of the primary flow 18 and the secondary flow 20.
  • the rotor 12 comprises several rows of rotor blades 24, in this case three.
  • the rotor vanes 24 may extend radially from a dovetail platform, or from a bladed one-piece drum inner ring.
  • the compressor 4 comprises several rectifiers, in this case four, each containing a row of stator vanes 26.
  • the rectifiers are associated with the fan 16 or a row of rotor blades to straighten the flow of air, so as to convert the speed of the flow pressure, especially static pressure.
  • the stator vanes 26 extend essentially radially from an outer casing 28. They can be fixed and immobilized by means of fixing pins 30. They pass radially through the primary flow 18.
  • the stator vanes may be fixed rope by 28.
  • the blades of the same row are identical and aligned. Each row may comprise at least one blade (26; 24).
  • Internal ferrules 32 may be suspended at the inner ends of the stator vanes 26.
  • the inner ferrules 32 may cooperate sealingly with the rotor 12.
  • the figure 3 sketching two blades (26A; 26B) representative of an annular row.
  • the row may be one of the rows presented in connection with the preceding figures.
  • the blades (26A, 26B) and their support, optionally the inner ferrule 32, are shown in plan.
  • the axis of rotation 14 is drawn at a figurative position to provide a spatial marker.
  • Each blade (26A; 26B) comprises a leading edge 34, a trailing edge 36, and a bottom surface 38 and an extrados surface 40. These surfaces (38; 40) can be curved and curved respectively. Each of these surfaces extends from the leading edge 34 to the corresponding trailing edge 36.
  • Each blade may comprise a stack of aerodynamic profiles 41 arched, the sides generate the intrados surface 38 and the extrados surface 40. At the trailing edges 36, the contours of the profiles 41, intrados and / or extrados, are parallel and / or tangent to the axis of rotation 14 of the compressor.
  • the consecutive blades (26A, 26B) of the annular row define between them a passage 42, also called an inter-blade passage 42.
  • This passage 42 is circumferentially partitioned by the blades (26A, 26B) and delimited by the intrados and extrados surfaces. .
  • the passage 42 may have a guide surface 44 between the two consecutive blades (26A; 26B), and may connect the intrados surface 38 which faces the extrados surface 40 through the passage 42.
  • the guide surface 44 may be defined axially by an upstream axis 46 and a downstream axis 48 which connect the leading edges 34 and the trailing edges 36 respectively. These axes (46; 48) can be parallel, and can generally define a parallelogram or a trapezoid.
  • the guide surface 44 may be generally planar.
  • the guide surface 44 may be a tubular surface portion or a cone surface portion, in particular because of the radius of the ferrule and the optional diameter variation of the ferrule 32 along the axis of the ferrule. rotation 14. It may comprise four corners 50 corresponding to the intersections between the edges (34; 36) and the support, in this case the ferrule 32, for example internal.
  • the guide surface 44 has an axially symmetrical zone 52, possibly substantially or flat, which passes axially through the passage 42.
  • the axisymmetric zone 52 may be formed of arcs 53 of constant radii around the axis of rotation 14, or according to the circumference . Some of the arches 53 extend circumferentially from the intrados surface 38 to the extrados surface 40.
  • the guiding surface 44 may be predominantly formed of these arches 53.
  • the guiding surface 44 also comprises a main recess 54 with a bottom 56 forming radially its extremum, and a main boss 58 with a peak 60 radially forming its extremum.
  • the main depression 54 and the main boss 58 are "main" insofar as they respectively form the main hollow and bulge, and / or area, and / or height of the guide surface 44.
  • the hollow 54 and the boss 58 may be at the same level axially; they can run axially.
  • the bottom 56 and the top 60 may coincide axially.
  • Some arches 53 may extend from the recess 54 to the boss 58.
  • the axisymmetric zone 52 circumferentially separates the recess 54 from the boss 58, while passing through the passage 42.
  • the axisymmetric zone 52 may comprise a circumferential narrowing 66 between the Hollow 54 and the hump 58. This narrowing 66 can form the lesser axial portion of the axisymmetric zone 52.
  • the hollow 54 and the hump 58 are represented using level lines 62. These level lines 62 show radial level variations with respect to a reference surface, in this case the guide surface 42, and in particular with respect to the axisymmetric zone 52.
  • the hollow 54 and the bump 58 may extend over at most the axial majority of the blades (26A; 26B).
  • the hump 58 may be longer than the recess 54. It may extend axially over 35%, +/- 5%, of the rope 64 of the second blade 26B.
  • the hollow 54 may extend axially 25%, +/- 5%, of the rope 64 of the first blade 26A.
  • the axisymmetric zone 52 may comprise an upstream section 47 extending downstream from the upstream axis 46, and a downstream section 49 extending upstream from the downstream axis 48.
  • the hollow 54 and the bump 58 may be distant from the leading edges 34, including 10% axial length of a rope 64. They are separated by the upstream section 47 can form a parallelogram.
  • the hollow 54 may extend over 15% of the inter-blade passage 42 and extend from the intrados surface 38. Its bottom 60 may be against the intrados surface 38.
  • the boss 58 may extend circumferentially on 20% of the passage 42, its top 60 can be attached to the extrados surface 40 of the second blade 26B.
  • Each blade (26A; 26B) comprises a rope 64 and a space 68 between its intrados surface 38 and its rope 64.
  • Each bottom 56 of recesses 54 may be inside said space 68.
  • each recess 54 is predominantly, or totally within the corresponding space 68.
  • between 40% and 80% of each recess 54 is within the corresponding space 68.
  • the figure 4 is a section of the figure 3 along the IV-IV axis.
  • the inclination of the axis of rotation 14 relative to the support is figurative and may vary in practice.
  • the blades may comprise connecting radii 70 at their radial ends. Each connection radius 70 may surround its respective blade.
  • the guide surface 44 may extend from the connecting spokes 70 so as to connect them in pairs.
  • the radial thickness of the connecting radii 70 is smaller than the height H of the boss 58 and the depth P of the recess 54.
  • the leading edge 34 and the trailing edge 36 of the first blade 26A extending radially from the annular surface 33 of the inner ferrule 32.
  • ring 33 may have a constant radius RC outside the non-axisymmetric zone 72 receiving the hump and the hollow; where the variable radius RV evolves according to the angular position about the axis of rotation 14.
  • the annular surface 33 may have axial symmetry.
  • the zones 47 and 49 can extend the annular surface 33 and be axially tangential thereto. They may have constant radius arcs RC depending on the circumference.
  • a mixed line 74 extends the zones 47 and 49, and connects them.
  • the hollow 54 in the background is represented by a dotted line.
  • the radial distance between the mixed line 74 and the hollow 54 or the bump 58, respectively, highlights their radial dimensions, ie the maximum depth reached by the bottom 56, and the maximum height occupied by the top 60. be joined by a line 76 also passing through the bottom 56, which emphasizes the axial alignment of these extremes.
  • the present teaching can also be applied to an outer shell or to the outer casing by symmetry axis A-A.
  • the figure 5 is a section of the figure 3 along the VV axis.
  • the section is perpendicular to the axis of rotation 14, and passes through the hollow 54 and the bump 58.
  • the guide surface 44 has a constant radius RC in contact with the arc 53 of the axisymmetric zone 52.
  • This constant radius RC may correspond to that of the first zone 47 and / or to that of the second zone 49.
  • RV variable radius
  • the guide surface 44 is profiled. It has an increase of radial material relative to its base, in particular generated by the zones (47; 49).
  • the radius RV of the guide surface 44 can fluctuate as it angularly traverses the joining surface 44 in the circumferential direction 15, in particular by moving from the first blade 26A to the second blade 26B, or between the intrados surface 38 and the extrados surface 40.
  • the present teaching can be applied to any one or more, or at each annular row of compressor blades.
  • the guide surface can be reproduced identically between each dawn nearby. This can form several annular rows of identical bumps and identical hollows.
  • the support may be replaced by blade attachment platforms.
  • Each blade (26A; 26B) can be associated with an individual attachment platform.
  • the lateral edges of the platforms marry, and each form a part of axisymmetric zone.
  • the teachings of each figure may be independently combined with the teachings of each of the other figures.
  • the invention provides a combination of the teachings of all the figures and / or with a combination of the whole of the technical solution.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP18195628.5A 2017-10-26 2018-09-20 Verdichter einer turbomaschine mit asymmetrisch konturiertem strömungsring Active EP3477050B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
BE2017/5765A BE1025667B1 (fr) 2017-10-26 2017-10-26 Virole asymetrique pour compresseur de turbomachine

Publications (2)

Publication Number Publication Date
EP3477050A1 true EP3477050A1 (de) 2019-05-01
EP3477050B1 EP3477050B1 (de) 2022-03-02

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EP18195628.5A Active EP3477050B1 (de) 2017-10-26 2018-09-20 Verdichter einer turbomaschine mit asymmetrisch konturiertem strömungsring

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US (1) US10787909B2 (de)
EP (1) EP3477050B1 (de)
BE (1) BE1025667B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3812548A1 (de) 2019-10-25 2021-04-28 Safran Aero Boosters SA Kompressorstufe einer strömungsmaschine mit optimierter innenendwand
BE1027711A1 (fr) 2019-10-25 2021-05-20 Safran Aero Boosters Sa Etage de compresseur de turbomachine

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KR20190046118A (ko) * 2017-10-25 2019-05-07 두산중공업 주식회사 터빈 블레이드
US11725526B1 (en) 2022-03-08 2023-08-15 General Electric Company Turbofan engine having nacelle with non-annular inlet

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WO2009112776A2 (fr) * 2008-02-28 2009-09-17 Snecma Aube avec plateforme non axisymetrique : creux et bosse sur extrados
EP2597257A1 (de) * 2011-11-25 2013-05-29 MTU Aero Engines GmbH Beschaufelung
EP2696029A1 (de) * 2012-08-09 2014-02-12 MTU Aero Engines GmbH Schaufelgitter mit Seitenwandkonturierung und Strömungsmaschine
WO2014105270A2 (en) * 2012-12-18 2014-07-03 United Technologies Corporation Airfoil assembly with paired endwall contouring
FR3011888A1 (fr) 2013-10-11 2015-04-17 Snecma Piece de turbomachine a surface non-axisymetrique
DE102015224376A1 (de) * 2015-12-04 2017-06-08 MTU Aero Engines AG Schaufelkanal, Schaufelgitter und Strömungsmaschine

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US3326523A (en) * 1965-12-06 1967-06-20 Gen Electric Stator vane assembly having composite sectors
GB0518628D0 (en) * 2005-09-13 2005-10-19 Rolls Royce Plc Axial compressor blading
US8206115B2 (en) * 2008-09-26 2012-06-26 General Electric Company Scalloped surface turbine stage with trailing edge ridges
FR2950942B1 (fr) * 2009-10-02 2013-08-02 Snecma Rotor d'un compresseur de turbomachine a paroi d'extremite interne optimisee

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Publication number Priority date Publication date Assignee Title
WO2009112776A2 (fr) * 2008-02-28 2009-09-17 Snecma Aube avec plateforme non axisymetrique : creux et bosse sur extrados
EP2597257A1 (de) * 2011-11-25 2013-05-29 MTU Aero Engines GmbH Beschaufelung
EP2696029A1 (de) * 2012-08-09 2014-02-12 MTU Aero Engines GmbH Schaufelgitter mit Seitenwandkonturierung und Strömungsmaschine
WO2014105270A2 (en) * 2012-12-18 2014-07-03 United Technologies Corporation Airfoil assembly with paired endwall contouring
FR3011888A1 (fr) 2013-10-11 2015-04-17 Snecma Piece de turbomachine a surface non-axisymetrique
DE102015224376A1 (de) * 2015-12-04 2017-06-08 MTU Aero Engines AG Schaufelkanal, Schaufelgitter und Strömungsmaschine

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3812548A1 (de) 2019-10-25 2021-04-28 Safran Aero Boosters SA Kompressorstufe einer strömungsmaschine mit optimierter innenendwand
BE1027709A1 (fr) 2019-10-25 2021-05-20 Safran Aero Boosters Sa Etage de compresseur de turbomachine
BE1027711A1 (fr) 2019-10-25 2021-05-20 Safran Aero Boosters Sa Etage de compresseur de turbomachine

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BE1025667B1 (fr) 2019-05-27
EP3477050B1 (de) 2022-03-02
US20190128122A1 (en) 2019-05-02
BE1025667A1 (fr) 2019-05-21
US10787909B2 (en) 2020-09-29

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